RU2275746C1 - Radio-technical reconnaissance station - Google Patents

Abstract

FIELD: radio engineering, possible radio-technical reconnaissance of radio-electronic means of enemy.

SUBSTANCE: radio-technical reconnaissance station contains antenna device 1, receiver 2, bearing device 3, analyzer 4 of received signal parameters, device 5 for memorizing and processing received information, telemetric device 6, receiving antennae 7-9, block 10 for readjustment, first 11 and second 23 heterodynes, mixers 12-14 and 24, amplifiers 17-19 of first intermediate frequency, detector 20, first 21 and second 31 delay lines, key 22, amplifier 25 of second amplification frequency, multipliers 26,27 and 30, narrowband filters 28,29 and 32, phase detector 33, phase meters 34 and 35, engine 15 and supporting generator 16.

EFFECT: expanded area of reconnaissance and increased number of detected radio-electronic means due to positioning of radio-technical reconnaissance station onboard the helicopter.

3 dwg

Description

The proposed station belongs to the field of radio engineering and allows radio-technical reconnaissance of radio electronic means (RES) of the enemy (radar, radio communications and control, etc.).

Known stations and systems for radio-technical reconnaissance of radiation from enemy RES (RF patent No. 2150178; US patents No. 3.806.926, 3.891.989, 3.896.439; German patent No. 3.346.155; British patent No. 1.587.357; French patent No. 2.447. 041; Vakin S.A., Shustov L.N. Fundamentals of Radio Countermeasures and Radio Engineering Intelligence (Moscow: Sov. Radio, 1968, p. 382, Fig. 10.2, etc.).

Of the known stations and systems, the closest to the proposed one is the radio intelligence station (Vakin SA, Shustov LN Fundamentals of radio resistance and radio intelligence. M: Sov. Radio, 1968, p. 382, Fig. 10.2), which and selected as the base.

The specified station contains a series-connected antenna device 1, receiver 2, an analyzer 4 of the parameters of the received signal, a device 5 for storing and processing the received information, the second input of which through a direction finding device 3 is connected to the output of the receiver 2, and a telemetry device 6, the output of which is the output of the station ( figure 1).

The disadvantage of this station is the limited area of intelligence.

An object of the invention is to expand the field of reconnaissance in terms of area and number of reconnaissance electronic equipment by placing a radio intelligence station on board a helicopter.

The problem is solved in that in a radio intelligence station containing a direction-finding device and a series-connected antenna device, a receiver, an analyzer of parameters of the received signal, a device for storing and processing the received information and a telemetry device, the output of which is the output of the station, the receiver is made in the form of a series-connected receiving antenna, the first bias, the second input of which is connected through the first local oscillator to the output of the tuning block, the amplifier of the first of an intermediate frequency, of a detector, the second input of which is connected to its output through the first delay line, a key, the second input of which is connected to the output of the amplifier of the first intermediate frequency, the second bias, the second input of which is connected to the output of the second local oscillator, and the amplifier of the second intermediate frequency, the output of which is the receiver output, the control input of the tuning unit is connected to the detector output, the direction-finding device is made in the form of two direction-finding channels, each of which consists of a follower of the newly included receiving antenna, a mixer, the second input of which is connected to the output of the first local oscillator, an amplifier of the first intermediate frequency, a multiplier, the second input of which is connected to the output of the amplifier of the second intermediate frequency, and a narrow-band filter, while the third multiplier is connected in series to the output of the first narrow-band filter, the second input of which is connected to the output of the second narrow-band filter, the third narrow-band filter and the first phase meter, to the output of the second narrow-band filter in series the second delay line is turned on, a phase detector, the second input of which is connected to the output of the second narrow-band filter, and the second phase meter, the second inputs of the phase meters are connected to the output of the reference generator, and the outputs are connected to a device for storing and processing the received information, the antenna device contains three receiving antennas, a receiving the receiver antenna is located above the rotor hub of the helicopter, the receiving antennas of the direction-finding device are located at the ends of the rotor blades of the helicopter, the engine is kinematically connected to the rotor m helicopter and reference generator.

The structural diagram of the proposed radio intelligence station is presented in figure 2, the geometric arrangement of the receiving antennas on the helicopter is shown in figure 3.

The receiver 2 contains a series-connected receiving antenna 7, a first bias 12, the second input of which through the first local oscillator 11 is connected to the output of the tuner 10, an amplifier 17 of the first intermediate frequency, a detector 20, the second input of which is connected to its output through the first delay line 21, the key 22, the second input of which is connected to the output of the amplifier 17 of the first intermediate frequency, the second bias 24, the second input of which is connected to the output of the local oscillator 23, and the amplifier 25 of the second intermediate frequency, the output of which is the output th receiver 2 and connected to the analyzer input signal 4 received parameters.

The direction-finding device 3 contains two direction-finding channels, each of which contains a receiving antenna 8 (9) sequentially connected, an offset 13 (14), the second input of which is connected to the output of the local oscillator 11, an amplifier 18 (19) of the first intermediate frequency, a multiplier 26 (27) , the second input of which is connected to the output of the amplifier 25 of the second intermediate frequency, and a narrow-band filter 28 (29). At the same time, the third multiplier 30 is connected in series to the output of the first narrow-band filter 28, the second input of which is connected to the output of the second narrow-band filter 29, the third narrow-band filter 32 and the first phase meter 34, the second delay line 31, the phase detector 33 are connected in series to the output of the second narrow-band filter 29 , the second input of which is connected to the output of the narrow-band filter 29, and the second phase meter 35. The second inputs of the phase meters 34 and 35 are connected to the output of the reference generator 16, and the outputs are connected to the storage device 5 processing the information received. The antenna device 1 contains three receiving antennas 7-9, the receiving antenna 7 of the receiver 2 is located above the rotor hub of the helicopter, the receiving antennas 8 and 9 of the direction-finding device 3 are located at the ends of the rotor blades of the helicopter (Fig. 3). The engine 15 is kinetically connected with the helicopter propeller and the reference generator 16.

The radio intelligence station operates as follows.

The station is located on board a helicopter. The presence of a rotary rotor of the helicopter is used to determine the direction to the radiating RES using an antenna device 1, receiving antennas 8 and 9 of which are located at the ends of the rotor blades (Fig. 3).

Signals received by antennas 7-9, for example with phase shift keying (PSK)

where U ₁ , U ₂ , U ₃ - amplitude signal RES;

ω _C is the carrier frequency of the RES signal;

φ is the initial phase of the RES signal;

t _with - the duration of the signal RES;

± Δω - instability of the carrier frequency of the signal due to various destabilizing factors;

φ _k (t) = {0, π} is the manipulated component of the phase, which displays the law of phase manipulation in accordance with the modulating code;

R is the radius of the circle on which the receiving antennas 8 and 9 are located;

 Ω = 2πR — rotation speed of receiving antennas 8 and 9 around receiving antenna 7 (rotational speed of a helicopter rotor);

α - bearing (azimuth) to the radiating RES,

arrive at the first inputs of the mixers 12-14, the second inputs of which the voltage of the first local oscillator 11 is linearly measured frequency

- скорость изменения частоты гетеродина.Where

- rate of change of the local oscillator frequency.

It should be noted that the search-PSK signal RES enemy in a predetermined frequency band _f D is carried out via adjustment assembly 10, which are periodically with period T _P sawtooth _G1 changes the frequency ω LO 11. As the adjustment unit 10 can be used by the sawtooth generator.

At the output of the mixers 12-14, voltages of combined frequencies are generated. Amplifiers 17-19 distinguish the voltage of the first intermediate frequency:

Where

To ₁ - gear ratio of the mixers;

ω _PR1 = ω _C -ω _G1 - the first intermediate frequency;

φ _PR1 = φ _C -φ _G1 .

The voltage U _PR1 (t) from the output of the amplifier 17 of the first intermediate frequency is supplied to the input of the detector 20. When a RES signal is detected, a constant voltage appears at the output of the detector 20, which is supplied to the control input of the tuning unit 10, turning it off, to the control input of the key 22, opening him, and to the input of the delay line 21. The key 22 in the initial state is always closed. The delay time τ _{3 of} the delay line is selected so that it is possible to fix the detected PSK signal and analyze its parameters.

When you turn off the tuning unit 10 amplifiers 17-19 allocated the following voltages:

The voltage U _PR4 (t) from the output of the amplifier 17 of the first intermediate frequency through the public key 22 is supplied to the first input of the mixer 24, the second input of which is supplied with the voltage of the second local oscillator 23 with a stable frequency ω _Г2

At the output of the mixer 24, a voltage of combination frequencies is generated. Amplifier 25 isolates the voltage of the second intermediate frequency

Where

ω _PR2 = ω _{PR1 -ω G2} - the second intermediate frequency;

φ _PR2 = φ _PR1 -φ _G2 ,

which is fed to the input of the analyzer 4 parameters of the received signal, which determines the duration τ _{3 of the} elementary parcels from which the PSK signal is composed, their number N (T _c = N τ _e ) and the law of phase manipulation.

The voltage U _PR7 (t) from the output of the amplifier 25 of the second intermediate frequency is simultaneously supplied to the second inputs of the multipliers 26 and 27 direction-finding channels, the first inputs of which receive the voltage U _PR5 (t) and U _PR6 (t) from the outputs of the amplifiers 18 and 19 of the first intermediate frequencies respectively. At the outputs of the multipliers 26 and 27, phase-modulated (FM) voltages are formed at a stable frequency ω _{Г2 of the} second local oscillator:

Where

To ₂ is the transmission coefficient of the multipliers, which are allocated by narrow-band filters 28 and 29 with the tuning frequency ω _H = ω _Г2.

соответствуют диаметрально противоположным расположениям антенн 8 и 9 на концах лопастей несущего винта вертолета относительно приемной антенны 7, размещенной над втулкой винта вертолета.Signs "+" and "-" before the value

correspond to diametrically opposite locations of the antennas 8 and 9 at the ends of the rotor blades of the helicopter relative to the receiving antenna 7 located above the hub of the helicopter rotor.

Therefore, useful information about the bearing α is transferred to the stable frequency ω _{Г2 of the} second local oscillator 23. Therefore, the instability ± Δω of the carrier frequency caused by various destabilizing factors and the type of modulation (manipulation) of the received RES signal do not affect the direction finding result, thereby increasing the accuracy of determination location of RES.

и называемая индексом фазовой модуляции, характеризует максимальное значение отклонения фазы сигналов, принимаемых вращающимися антеннами 8 и 9 относительно фазы сигнала, принимаемого неподвижной антенной 7.Moreover, the value that is part of these fluctuations

and called the phase modulation index, characterizes the maximum value of the phase deviation of the signals received by the rotating antennas 8 and 9 relative to the phase of the signal received by the fixed antenna 7.

The direction-finding device 3 is the more sensitive to a change in the angle α, the larger the relative size of the measuring phase R / λ. However, with increasing R / λ, the value of the angular coordinate α decreases, at which the phase difference exceeds 2π, i.e. ambiguity of reading the angle α occurs.

наступает неоднозначность отсчета угла α. Устранение указанной неоднозначности путем уменьшения соотношения

обычно себя не оправдывает, так как при этом теряется основное достоинство широкобазовой системы. Кроме того, в диапазоне метровых и особенно дециметровых волн брать малые значения

часто не удается из-за конструктивных соображений.Therefore, for

ambiguity of reading the angle α occurs. Resolving this ambiguity by reducing the ratio

usually doesn’t justify itself, since the main advantage of the wide-base system is lost. In addition, in the range of meter and especially decimeter waves, take small values

often fails due to design considerations.

To increase the accuracy of the direction finding of the RES in the horizontal (vertical) plane, the receiving antennas 8 and 9 are located at the ends of the rotor blades of the helicopter. The mixing of signals from two diametrically opposite receiving antennas 8 and 9, located at the same distance R from the axis of rotation of the rotor, causes phase modulation obtained using one receiving antenna rotating in a circle whose radius R is two times larger (R ₁ = 2R )

Indeed, the output of the multiplier 30 produces a harmonic voltage

Where

with phase modulation index

which is allocated by a narrow-band filter 32 and fed to the first input of the phasemeter 34, the second input of which is supplied with the voltage of the reference oscillator 16

U ₀ (t) = U ₀ cos Ωt.

The phasometer 34 provides an accurate but ambiguous measurement of the angular coordinate α.

. Это достигается использованием автокоррелятора, состоящего из линии задержки 31 и фазового детектора 33, что эквивалентно уменьшению индекса фазовой модуляции до величиныTo eliminate the ambiguity in reading the angle α, it is necessary to reduce the phase modulation index without decreasing the ratio

. This is achieved by using an autocorrelator consisting of a delay line 31 and a phase detector 33, which is equivalent to reducing the phase modulation index to

where d ₁ <R.

A voltage is generated at the output of the autocorrelator

with the phase modulation index Δφ _m2 , which is supplied to the first input of the phasemeter 35, the voltage U ₀ (t) of the reference generator 16 is supplied to the second input. The phase meter 35 provides a rough but unambiguous measurement of the angle α.

The minimum distance R ₀ from the RES to the helicopter propeller is determined from the expression

F _g (t) ≈ (V ² · t ² ) / (λ · R ₀ ),

where F _g (t) is the Doppler frequency shift;

V = Ω · R;

λ is the wavelength.

The Doppler frequency shift is measured in the analyzer 4 parameters of the received signal, which also determines R ₀ . The latter are recorded in the device 5 for storing and processing the received information.

The location of the RES is determined in the device 5 by the measured values of α and R ₀ .

Telemetry device 6 is designed to transmit intelligence information to the control point.

After the time τ _{s, the} constant voltage from the output of the delay line 21 is supplied to the control input of the detector 20 and resets its contents to zero. In this case, the key 22 is closed, and the tuning unit 10 is turned on, i.e. they are translated into their original positions.

When a signal of the next enemy RES is detected, the operation of the radio intelligence station occurs in a similar way.

The helicopter flight path, on board of which a radio intelligence station is located, is usually laid in the border areas without violating the enemy’s airspace and without diplomatic complications.

Thus, the proposed radio intelligence station in comparison with the base provides the expansion of the field of intelligence in the area and the number of reconnaissance electronic equipment. This is achieved by placing a radio intelligence station on board the helicopter, the flight route of which is laid in the border areas without violating the enemy’s airspace and without diplomatic complications.

The proposed radio intelligence station provides accurate and unambiguous determination of the location of RES. Moreover, the direction-finding device is invariant to the type of modulation (manipulation) and instability of the carrier frequency of the received RES signals.

Claims (1)

A radio intelligence station containing a direction-finding device and a series-connected antenna device, a receiver, an analyzer of parameters of the received signal, a device for storing and processing the received information and a telemetry device, the output of which is the output of the station, characterized in that the receiver is made in the form of a series-connected receiving antenna, the first mixer, the second input of which through the first local oscillator is connected to the output of the tuning unit, the amplifier of the first intermediate frequency a detector, the second input of which is connected to its output through the first delay line, a key, the second input of which is connected to the output of the amplifier of the first intermediate frequency, a second mixer, the second input of which is connected to the output of the second local oscillator, and the amplifier of the second intermediate frequency, the output of which is the output receiver, the control input of the tuning unit is connected to the detector output, the direction-finding device is made in the form of two direction-finding channels, each of which consists of a series-connected reception antenna, mixer, the second input of which is connected to the output of the first local oscillator, an amplifier of the first intermediate frequency, a multiplier, the second input of which is connected to the output of the amplifier of the second intermediate frequency, and a narrow-band filter, while the third multiplier, the second input, are connected in series to the output of the first narrow-band filter which is connected to the output of the second narrow-band filter, the third narrow-band filter and the first phase meter, the second line is connected in series to the output of the second narrow-band filter delays, a phase detector, the second input of which is connected to the output of the second narrow-band filter, and the second phase meter, the second inputs of the phase meters are connected to the output of the reference generator, and the outputs are connected to a device for storing and processing the received information, the antenna device contains three receiving antennas, the receiving antenna of the receiver is located above the helicopter rotor hub, receiving antennas of the direction-finding device are located at the ends of the rotor blades of the helicopter, the engine is kinematically connected with the helicopter rotor and the reference generator.

Images